N819NY

Part: FITTING · airframe 48,618 hrs · 23,366 cycles

AFT SERVICE DOOR HOLD OPEN HOOK PAN ON DOOR CRACKED. REMOVED AND REPLACED HOOK PAN IAW SRM 51-40-02.

Part: SKIN · airframe 48,618 hrs · 23,366 cycles

AFT SERVICE DOOR OUTER SKIN CRACKED IN TWO PLACES AFT END OF HOLD OPEN HOOK WELL. REPAIRED DOOR SKIN PER ECRA 5205-01008 AND SRM 52-05, FIG 20A.

Part: ANGLE · airframe 48,619 hrs · 23,366 cycles

LT ATTACH ANGLE FOR VERTICLE TO FUSELAGE IS CRACKED AT STA 1474. INSTALLED REPAIR ON ATTACH ANGLE PER SRM 53-05 FIG 23 AND SRM 53-05 FIG 23A.

Part: BATTERY — DISCHARGED (CABIN) · airframe 45,234 hrs · 21,623 cycles

INSPECTION FOUND EMERGENCY OVERHEAD LIGHTS INOPERATIVE FROM ROWS 1-7. THE BATTERIES FOR THE OVERHEAD EMERGENCY LIGHTS WERE REMOVED AND REPLACED AND OPERATION CHECKED GOOD IAW MM 33-50-00.

Part: SENSOR — INOPERATIVE (NLG) · airframe 42,769 hrs · 20,288 cycles

THE NOSE GEAR RED UNSAFE LIGHT REMAINED ILLUMINATED AFTER GEAR RETRACTION ON TAKEOFF FROM IAH. CHECKLIST PROCEDURES WERE FOLLOWED AND THE GEAR WAS LOWERED AND RAISED. THE NOSE GEAR PIN ON PEDESTAL INDICATED NOSE GEAR WAS FULL DOWN. THE AIRCRAFT WAS RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NOSE GEAR UPLOCK SENSOR AT FAULT. THE NOSE GEAR UPLOCK SENSOR WAS REMOVED AND REPLACED IAW MM 32-60-05, PARAGRAPH 7. INDICATION AND OPERATIONAL CHECKS WERE GOOD.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND LT CENTER SEAT TRACK CORRODED ON FLOOR PANEL FLANGES AT STA 1145-1175, LBL 44. THE SEAT TRACK WAS REMOVED AND A NEW SEAT TRACK WAS INSTALLED IAW SRM 53-05, FIGURE 4, 51-10-4, AND 51-10-3.

Part: ATTACH ANGLE — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND L-1 DOOR LOWER AFT GIRT BAR ATTACH ANGLE CORRODED AT FS 200, LBL 54. THE ATTACH ANGLE WAS REMOVED AND A NEW ANGLE WAS INSTALLED IAW SRM 51-30-5, 51-10-4, AND 51-10-3.

Part: TRIM TAB — DENTED (RUDDER) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND RT SIDE OF RUDDER TRIM TAB DENTED. THE TRIM TAB WAS REMOVED AND REPLACED IAW MM 27-20-02, PARAGRAPH 3A, B, C. A WEIGHT AND BALANCE WAS PERFORMED ON THE TAB IAW SRM 55-40-1 AND THE CHECK WAS WITHIN LIMITS.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND LT CENTER SEAT TRACK CORRODED AT STA 1145 - 1175, LBL 44. THE SEAT TRACK WAS REMOVED AND A NEW SEAT TRACK WAS INSTALLED IAW SRM 53-05, FIGURE 4, 51-10-4, AND 51-10-3.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND A 2 INCH CRACK IN AFT CARGO DOOR FORWARD UPLOCK ANGLE AT FS 1720, LBL 40. THE ANGLE WAS REMOVED AND A NEW ANGLE WAS INSTALLED IAW SRM 51-30-2 AND 51-10-4.

Part: SKIN PANEL — CORRODED (HORIZONTAL STAB) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND THAT THE LT AND RT HORIZONTAL STABILIZERS HAD BARREL NUT HOLES CORRODED WITH MISSING SEALANT. THE CORRODED BARREL NUTS AND PLI WASHERS WERE REMOVED AND REPLACED IAW MM 20-10-14. THE CORROSION WAS REMOVED AND BUSHINGS WERE INSTALLED IAW ECRA 5510-01531. THE BARREL NUT HOLES WERE RESEALED IAW MM 20-20-03.

Part: SKIN — CANNING (CARGO DOOR) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND AFT CARGO DOOR EXTERIOR SKIN OIL CANNING AND DENTED BELOW AFT HINGE. THE AFT DOOR ARM WAS REMOVED IAW MM 52-31-01. REMOVED WEB IAW SRM 51-10-4. THE DAMAGED AREA WAS CUT OUT IAW SRM 52-05, FIGURE 3. A DOUBLER WAS INSTALLED IAW SRM 52-05, FIGURE 3, 51-30-2, AND 51-30-5. THE WEB WAS INSTALLED IAW SRM 51-30-2 AND 51-30-5. THE DOOR HINGE WAS REINSTALLED IAW MM 52-31-01.

Part: SKIN — DENTED (CARGO DOOR) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND FORWARD CARGO DOOR OUTER SKIN AFT MID EDGE DENTED AND TORN. A REPAIR DOUBLER WAS INSTALLED IAW SRM 51-10-4, 51-10-3, 51-30-2, EA 9-5231-2-A0724, AND ECRA 5230-01559.

Part: BRACKET — CRACKED (SLAT TRACK) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND A 1 INCH CRACK IN RT WING NR 1 SLAT TRACK LOWER FAIRING I/B BRACKET. THE BRACKET WAS REMOVED AND A NEW BRACKET WAS INSTALLED IAW SRM 51-30-01, 51-10-04, 51-10-3.

Part: SKIN — CRACKED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND A 1 INCH CRACK IN FORWARD CARGO DOOR JAMB SKIN AT APPROXIMATELY 20 FROM FORWARD LOWER CORNER, FS 389, LONGERON 27R. A FILLER AND DOUBLER WERE INSTALLED IAW SRM 53-05, FIGURE 82, 51-30-2, AND 51-30-5.

Part: SKIN — CORRODED (LT WING) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND LT WING LOWER SKIN CORRODED AT MID BUTT, XFS 170 - XFS 290. THE AREA WAS REPAIRED IAW EA 9-5731-2-A0711 AND ECRA 5730-01700.

Part: SKIN — DAMAGED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND RADOME TO FUSELAGE SKIN DAMAGED AT FS 37, BL 0. THE RADOME WAS REMOVED IAW MM 53-51-00 AND THE DAMAGED AREA WAS CUT OUT. FILLER AND DOUBLER WERE INSTALLED IAW ECRA 5330-02968 AND EA 9-5331-2-A0718. THE RADOME WAS REINSTALLED IAW MM 53-51-00.

Part: SKIN — CORRODED (LT WING) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND LT WING SKIN CORRODED AT XFS 164 - XFS 267. REPAIRED AREA IAW ECRA 5730-01700.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND A 2 INCH CRACK IN VERTICAL STABILIZER TO FUSELAGE ATTACH ANGLE AT RT AFT END, STA 1275. FASTENERS WERE REMOVED AND THE CRACKED AREA WAS CUT OUT IAW SRM 51-30-5 AND 53-05, FIGURE 23. AN ANGLE REPAIR WAS INSTALLED IAW SRM 53-05, FIGURE 23, 51-10-3, 51-10-4, 51-10-3, AND 51-30-5, FIGURE 23.

Part: SKIN — CORRODED (RT WING) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND RT WING LOWER SKIN SURFACE CORRODED JUST O/B OF VORTILON AT XCW62-XRS 335. THE SKIN WAS REPAIRED IAW ECRA 5730-01700.

Part: SKIN — CORRODED (RT WING) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND RT WING LOWER SKIN SURFACE CORRODED JUST FORWARD OF NR 2 FLAP HINGE AT XRS 111.5. REPAIRED IAW SRM 57-03, FIGURE 24A, SHEET 4 AND ECRA 5730-01694.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND LT TIE DOWN TRACK CORRODED UNDER NUT CLIPS IN FORWARD PIT AT FS 218 - 538, LONGERON 27L. THE TIE DOWN TRACK WAS REMOVED AND A NEW TRACK WAS INSTALLED IAW SRM 51-30-1, 51-30-2, AND 51-30-5.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND RIGHT O/B SEAT TRACK CORRODED AT STA 720 - 795, RBL 54.5. THE SEAT TRACK WAS REMOVED AND A NEW SEAT TRACK WAS INSTALLED IAW SRM 51-10-4, 51-10-3, 53-05, FIGURE 4F, 51-30-1, AND 51-30-5.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND MID CARGO DOOR CUTOUT FLOORBEAM CORRODED AT FS 636 - 712, LONGERON 27R. THE BEAM WAS REMOVED AND REPLACED IAW SRM 51-30-02 AND 51-30-05. FLOOR SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-30-02.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND FLOOR SUPPORTS CORRODED IN MID CARGO AREA AT STA 522 BETWEEN LONGEROSN 28L & 28R AND BETWEEN LONGERON 24L & 24R. THE FLOOR SUPPORTS WERE REMOVED AND NEW FLOOR SUPPORTS WERE INSTALLED IAW SRM 51-30-2.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND LT TIE DOWN TRACK CORRODED IN AFT CARGO AREA AT FS 1007 - 1320, LONGERON 27L. THE TIE DOWN TRACK AND SPLICE WERE REMOVED AND A NEW TRACK AND SPLICE WERE INSTALLED IAW SRM 51-30-1, 51-30-2, 51-10-4, AND 53-05, FIGURE 4B.

Part: SKIN — CORRODED (TE FLAP) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND LT WING LOWER SKIN CORRODED AT NR 1 FLAP HINGE, XRS 111.5. A REPAIR DOUBLER AND FILLER WERE INSTALLED IAW EA 9-5731-2-A0700 AND ECRA 5730-01695.

Part: SKIN — DENTED (AILERON) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND LT AILERON UPPER SURFACE DENTED. A DOUBLER WAS INSTALLED IAW SRM 57-01. AN ADJUSTMENT TEST OF AILERON TRIM AND CONTROL TABS WAS PERFORMED IAW MM 27-10-05.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND LT TIE DOWN TRACK CORRODED IN MID CARGO AREA AT STA 522 - 786.5, LONGERON 27L. THE TIE DOWN TRACK WAS REMOVED AND REPLACED IAW SRM 51-30-2 AND 51-30-5.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND FLOOR SUPPORTS CORRODED IN MID CARGO AREA AT FS 693 - 731, LONGERON 27R AND AT FS 786 BETWEEN LONGERON 28L AND 28R. THE FLOOR SUPPORTS WERE REMOVED AND NEW SUPPORTS WERE INSTALLED IAW SRM 51-10-4, 51-10-3, 51-30-2, AND 51-30-1.

Part: FITTING — CRACKED (CARGO DOOR) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND A 2 INCH CRACK IN MID CARGO DOOR LOWER FORWARD STOP INNER SUPPORT FITTING. THE FITTING WAS REMOVED AND A NEW FITTING WAS INSTALLED IAW SRM 51-30-2, 51-10-4, AND 51-30-1.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND LEFT I/B SEAT TRACK CORRODED AT FS 1207, LBL 24. THE SEAT TRACK WAS REMOVED AND REPLACED IAW SRM 51-30-1, 51-30-5, AND 53-05, FIGURE 4F.

Part: ATTACH ANGLE — CORRODED (PAX DOOR) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND L-1 DOOR LOWER AFT GIRT BAR ATTACH ANGLE CORRODED, BS 200, LBL 54. THE ANGLE WAS REMOVED AND A NEW ANGLE WAS INSTALLED IAW SRM 51-30-5, 51-10-4, AND 51-10-3.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND LEFT O/B SEAT TRACK CORRODED AT STA 1174, LBL 52.5. THE SEAT TRACK WAS REMOVED AND A NEW SEAT TRACK WAS INSTALLED IAW SRM 51-30-2.

Part: ANGLE — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND RIGHT CARGO TRACK Z-ANGLE CORRODED IN FORWARD PIT JUST AFT OF DOOR, FS 427, LONGERON 27R. THE Z-ANGLE AND A SUPPORT ANGLE WERE REMOVED AND NEW ANGLES WERE INSTALLED IAW SRM 51-30-2, 51-30-5, AND 51-30-1.

Part: GALLEY TRACK — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND G-1 GALLEY SUPPORT FITTING CORRODED AT FS 160, RBL 14. THE SUPPORT FITTING WAS REMOVED AND A NEW SUPPORT FITTING WAS INSTALLED IAW SRM 51-10-04, 51-10-03, 51-30-02, AND 51-30-05.

Part: BRACKET — CRACKED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND A 1.25 INCH CRACK IN WING TO BODY FAIRING ATTACH BRACKET AT FS 855, BL 0. THE BRACKET WAS REMOVED AND A NEW BRACKET WAS INSTALLED IAW SRM 51-30-5.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND LEFT I/B SEAT TRACK CORRODED AT STA 460, LBL 22. THE CORRODED SEAT TRACK WAS CUT OUT AND A NEW SEAT TRACK WAS INSTALLED IAW SRM 53-05, FIGURE 4B.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND LT CENTER SEAT TRACK CORRODED AT FS 1195, LBL 44. THE SEAT TRACK WAS REMOVED AND A NEW SEAT TRACK WAS INSTALLED IAW SRM 53-05, FIGURE 4F, AND 51-30-5.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND CABIN FLOOR SUPPORT CORRODED IN E & E COMPARTMENT AT STA 200 - 218, RBL 40 - 56. A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-01, FIGURE 4 AND 51-10-3. INSTALLED ANGLE AND FLOOR SUPPORT IAW SRM 51-30-2.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND MID CARGO TIE DOWN TRACK CORRODED AT FS 522 - 636, LONGERON 27R. THE TIE DOWN TRACK AND SPLICE WERE REMOVED AND A NEW TRACK AND SPLICE WERE INSTALLED IAW SRM 51-30-1, 51-30-2, 51-10-4, AND 53-05, FIGURE 4G.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND RT CENTER SEAT TRACK GOUGED AND CORRODED AT STA 225 - 235, RBL 22.5. THE SEAT TRACK WAS REMOVED AND REPLACED IAW SRM 51-30-05 AND 53-05, FIGURE 4F.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND AFT CARGO RT TIE DOWN TRACK CORRODED BETWEEN FS 1211 AND 1338, LONGERON 27R. THE TIE DOWN TRACK WAS REMOVED AND A NEW TRACK WAS INSTALLED IAW SRM 51-30-02.

Part: SKIN — GOUGED (CARGO DOOR) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND FORWARD CARGO DOOR NR 1 AND NR 14 STOP MOUNT SKIN GOUGED. REPAIR DOUBLERS WERE INSTALLED AT EACH LOCATION IAW ECRA 5330-02819.

Part: BEAM — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND AFT CARGO BAY LOWER DOOR JAMB BEAM CORRODED AT FS 1155 - 1212, LONGERON 27L. THE CORRODED SPACER AND DOUBLER WERE REMOVED AND REPLACED WITH A NEW SPACER AND DOUBLER IAW SRM 51-30-5, 51-30-1, 51-30-4, AND ECRA 5310-03027.

Part: FRAME — CRACKED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND A .25 INCH CRACK IN MAIN CABIN LT WINDOW FRAME AT FS 1022, L10L AND AT FS 946, L10L. THE WINDOW FRAMES WERE REPAIRED BY INSTALLING DOUBLER AND FILLER IAW ECRA 5330-02569, SRM 51-10-3, 51-30-2, AND 51-30-5.

Part: STOP — GOUGED (NR 1 ENGINE T/R) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND NR 1 ENGINE LOWER T/R STOP GOUGED. AN ANGLE AND CAP REPAIR WAS INSTALLED IAW SRM 51-30-2.

Part: PAN — CRACKED (CARGO DOOR) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND A 2 INCH CRACK IN AFT CARGO DOOR INNER PAN AT FORWARD ROLLER LOCK. THE CRACK WAS STOP DRILLED AND A REPAIR DOUBLER WAS INSTALLED IAW SRM 52-05, FIGURE 26A.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND CARGO TRACK IN FORWARD PIT CORRODED AT FS 351, LONGERON 27R. THE TRACK WAS REMOVED AND REPLACED IAW SRM 51-30-1 AND 51-30-2.

Part: SKIN — CRACKED (RT MLG DOOR) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND A 2 INCH CRACK IN REPAIR DOUBLER OF RT MLG DOOR AT I/B LOWER FORWARD CORNER. THE DOUBLER WAS REMOVED AND REPLACED IAW SRM 51-30-02.

Part: DOOR FRAME — CRACKED (MLG WW) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND A 1 INCH CRACK IN RT WHEEL WELL FORWARD I/B CORNER OF DOOR JAMB FRAME. THE DOOR JAMB FRAME WAS REMOVED AND REPLACED IAW SRM 51-30-02.

Part: FITTING — CORRODED (GIRT BAR) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND R-1 DOOR GIRT BAR FITTINGS CORRODED AT FS 160, RBL 54. THE GIRT BAR FITTINGS WERE REMOVED AND REPLACED IAW SRM 51-30-1.

Part: BRACKET — CRACKED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND A 1.5 INCH CRACK IN BRACKET JUST FORWARD OF RT WHEEL WELL HYDRAULIC BYPASS HANDLE, FS 785. THE BRACKET WAS REMOVED AND A NEW BRACKET WAS INSTALLED IAW SRM 51-30-05.

Part: SKIN — CRACKED (CARGO DOOR) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND A .5 INCH CRACK AND GOUGE IN FORWARD CARGO DOOR NR 12 STOP MOUNT RECESSED SKIN. A REPAIR DOUBLER WAS INSTALLED IAW ECRA 5330-02819.

Part: SKIN — CRACKED (NLG DOOR) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND THE RT AFT NOSE GEAR DOOR CORRODED ON INNER SKIN SURFACE WITH A 2 INCH CRACK AT LOWER EDGE OF DOOR. THE CORROSION WAS REMOVED IAW SRM 51-10-3 AND MATERIAL LOSS WAS FOUND WITHIN LIMITS IAW SRM 52-06. THE DOOR WAS REMOVED, THE CRACK WAS STOP DRILLED, AND A DOUBLER WAS INSTALLED IAW SRM 51-30-1 AND 52-01, FIGURE 2.

Part: STIFFENER — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND TORQUE BOX STIFFENER CORRODED AT FS 695, LONGERON 29R. REPAIRED IAW SRM 51-30-05.

Part: STRAP — GOUGED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND MID CARGO PIT FORWARD AND TORQUE BOX STRAP GOUGED AND CORRODED AT FS 638, LONGERON 27R AND FS 693, L27R. THE CORROSION WAS REMOVED IAW SRM 51-10-3. A NEW STRAP WAS INSTALLED IAW SRM 51-10-4, 51-10-3, AND 51-30-5.

Part: SEAT TRACK — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND LEFT I/B SEAT TRACK CORRODED ON FLANGES AT STA 1136 - 1174, LBL 22.5. THE SEAT TRACK WAS REMOVED AND A NEW SEAT TRACK WAS INSTALLED IAW SRM 51-10-4, 51-10-3, AND 53-05, FIGURE 4F.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND L-1 DOOR FLOOR SUPPORT AT FS 160 - 200, LBL 54 CORRODED. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-30-2, 51-10-4, 51-10-3, AND 51-30-5.

Part: STIFFENER — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND MID CARGO FORWARD TORQUE BOX STIFFENER CORRODED AT FS 655, L27R. A REPAIR WAS INSTALLED IAW SRM 51-30-05.

Part: ATTACH ANGLE — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND EPC PANEL ATTACH ANGLE CORRODED AT FS 160, LBL 10 - 20. THE ATTACH ANGLE WAS REMOVED AND REPLACED IAW SRM 51-30-02 AND THE PANEL WAS REINSTALLED IAW SRM 51-30-04.

Part: ANGLE — CRACKED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND A 3 INCH CRACK IN LT MLG WHEEL WELL AFT CUTOUT O/B SIDE SUPPORT ANGLE AT FS 1007, LBL 63. THE CRACK WAS STOP DRILLED AND A DOUBLER WAS INSTALLED IAW SRM 53-01.

Part: FLOORBEAM — CRACKED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND A 3 INCH CRACK IN FLOORBEAM AT FS 1309, LBL 54 AFTER REMOVAL OF LEFT O/B SEAT TRACK. A REPAIR WAS INSTALLED IAW SRM 51-30-05, 53-05, FIGURE 20A, AND 51-30-02.

Part: SKIN — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND E & E COMPARTMENT AFT WATER DRAIN CUTOUT CORRODED AT FS 207, BL 0. THE CORROSION WAS REMOVED IAW SRM 51-10-03. A NEW DOUBLER WAS INSTALLED IAW SRM 53-04, FIGURE 38, 51-10-03, AND 51-30-02.

Part: DOUBLER — CHAFED (LT MLG DOOR) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND LT MLG DOOR AFT LOWER CORNER REPAIR DOUBLER CHAFED. THE REPAIR DOUBLER WAS REMOVED AND A NEW DOUBLER WAS INSTALLED IAW SRM 51-30-02.

Part: PAN — CRACKED (CARGO DOOR) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND A .5 INCH CRACK IN MID CARGO DOOR INNER PAN AT FORWARD ROLLER LOCK. A REPAIR ANGLE WAS INSTALLED IAW SRM 52-05, FIGURE 26A.

Part: PAN — GOUGED (CARGO DOOR) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND FORWARD CARGO DOOR PAN GOUGED AT NR 5, 11, & 13 STOP MOUNTS. A REPAIR DOUBLER WAS INSTALLED AT EACH LOCATION IAW ECRA 5330-02819.

Part: FITTING — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND GALLEY 1 O/B SUPPORT FITTING CORRODED AT FS 160, RBL 44. THE SUPPORT FITTING AND FLOOR SUPPORT WERE REMOVED IAW SRM 51-30-02 AND 51-30-05. A NEW REPAIR FITTING WAS INSTALLED IAW SRM 51-10-04, 51-10-03, AND 51-30-05. THE FLOOR SUPPORT WAS INSTALLED IAW SRM 51-30-05.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND FLOORBEAM CORRODED AT FS 200, RBL 44 - 54. THE FLOORBEAM WAS REMOVED AND A NEW FLOORBEAM WAS INSTALLED IAW SRM 51-10-03, 51-10-04, 51-30-05.

Part: FLOOR SUPPORT — CHAFED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND CABIN FLOOR SUPPORT CHAFED AT STA 965, BL 0. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-20-03, 51-10-04, 51-10-03, AND 51-30-05.

Part: PAN — CRACKED (CARGO DOOR) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND 0.75 INCH CRACK IN AFT CARGO DOOR INNER PAN AT AFT ROLLER LOCK. THE AREA WAS REPAIRED IAW SRM 52-05, FIGURE 26A.

Part: SKIN PANEL — CRACKED (RT WING) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND A 3 INCH CRACK IN WING PANEL AT RT WING LOWER SURFACE JUST AFT OF MLG, WS 111. THE PANEL WAS REMOVED, REPAIRED AND REINSTALLED IAW SRM 51-30-02.

Part: PAN — GOUGED (CARGO DOOR) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND MID CARGO DOOR PAN GOUGED AT STOPS NR 1 THROUGH NR 5. A REPAIR DOUBLER WAS INSTALLED AT EACH LOCATION IAW ECRA 5330-02819, SRM 51-10-03, AND 51-30-03.

Part: DOUBLER — GOUGED (FUSELAGE SKIN) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND REPAIR DOUBLER GOUGED IN NOSE WHEEL WELL AT LT SIDE WALL BELOW TRUNNION FITTING, FS 101. THE REPAIR DOUBLER WAS REMOVED AND REPLACED IAW SRM 51-30-05.

Part: SEAT TRACK — GOUGED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND RIGHT I/B SEAT TRACK GOUGED AT STA 750, RBL 22. THE SEAT TRACK WAS REMOVED AND A REPAIR WAS INSTALLED IAW SRM 51-30-01 AND 53-05-04.

Part: WEB — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND SUB FLOOR WEB CORRODED AT FS 150 FROM RBL 46 TO RBL 52. A REPAIR DOUBLER WAS INSTALLED IAW ECRA 5320-01210, SRM 53-01, FIGURE 4, 51-30-02, AND 51-10-03.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND FLOOR SUPPORTS CORRODED AT STA 160, RBL 12 - 44 AND AT STA 140 - 160, RBL 34. THE FLOOR SUPPORTS WERE REMOVED AND NEW FLOOR SUPPORTS WERE INSTALLED IAW SRM 51-30-2.

Part: SKIN — BENT (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND RT AFT DOOR SHELF NOSE GEAR ATTACH ANGLE AND SKIN BENT AT FS 110. THE ATTACH ANGLE WAS REMOVED AND A NEW ANGLE WAS INSTALLED IAW SRM 51-30-2 AND 51-10-3.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND FLOOR SUPPORTS CORRODED AT STA 200, LBL 10 - 14 AND AT STA 218, LBL 14 - RBL 14. THE FLOOR SUPPORTS WERE REMOVED AND NEW FLOOR SUPPORTS WERE INSTALLED IAW SRM 51-30-2.

Part: CARGO TRACK — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND AFT CARGO RT TIE DOWN TRACK CORRODED BETWEEN FS 1007 AND 1155. THE TIE DOWN TRACK WAS REMOVED AND REPLACED IAW SRM 51-30-05 AND 53-05, FIGURE 46.

Part: WEB — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND LT CUSP WEB CORRODED ON UPPER SURFACE AT STA 1136 - 1174, LBL 46 - 56. THE CORROSION WAS REMOVED IAW SRM 51-10-3. THE AREA WAS REPAIRED BY INSTALLING A DOUBLER IAW SRM 53-01, FIGURE 2 AND 51-30-2.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND FLOOR SUPPORT CORRODED AT FS 160, BL 0. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-10-4, 51-30-5, AND 51-10- 3.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND FLOOR SUPPORTS CORRODED AT STA 140 - 200, LBL 8 AND STA 200, RBL 12 - 44. THE FLOOR SUPPORTS WERE REMOVED AND NEW FLOOR SUPPORTS WERE INSTALLED IAW SRM 51-30-2, 51-10-4, 51-30-1, AND 51-30-5.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND R-1 DOOR THRESHOLD FLOOR SUPPORT CORRODED AT FS 140 - 200, RBL 54. THE FLOOR SUPPORT WAS REMOVED AND A NEW FLOOR SUPPORT WAS INSTALLED IAW SRM 51-30-1, 51-10-4, AND 51-10-3.

Part: GALLEY TRACK — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND G-2 GALLEY SUPPORT CORRODED AT FS 209, RBL 14. THE SUPPORT WAS REMOVED AND A NEW SUPPORT WAS INSTALLED IAW SRM 51-10-4, 51-10-3, AND 51-10-5.

Part: ATTACH ANGLE — CRACKED (VERTICAL STAB) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND A 2 INCH CRACK IN LT DORSAL FIN INNER ATTACH ANGLE. THE ANGLE WAS REMOVED AND A NEW ANGLE WAS INSTALLED IAW SRM 51-30-02, 51-10-04, 51-10-03, AND 51-30-04.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND FLOORBEAM CORRODED AT FS 1155, LBL 22 - 44. THE BEAM WAS REMOVED AND A NEW BEAM WAS INSTALLED IAW SRM 51-10-04, 51-10-03, 51-30-01, AND 51-30-05.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND FLOORBEAM CORRODED AT FS 180, LBL 14-34. THE FLOORBEAM WAS REMOVED AND A NEW FLOORBEAM WAS INSTALLED IAW SRM 51-30-02, 51-10-04, AND 51-10-03.

Part: FLOORBEAM — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND SUBFLOOR WEB CORRODED AT FS 160 - 200, LB 12 - 44. A REPAIR DOUBLER WAS INSTALLED IAW SRM 53-01, FIGURE 4 AND 51-10-03.

Part: ATTACH ANGLE — CRACKED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND A 1 INCH CRACK IN WING TO BODY FAIRING ATTACH ANGLE AT STA 875, BL 0. THE ATTACH ANGLE WAS REMOVED AND REPLACED IAW SRM 51-30-05.

Part: FLOOR SUPPORT — CORRODED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND FLOOR SUPPORT CORRODED AT STA 200 - 218, LBL 14. THE FLOOR SUPPORT WAS REMOVED AND REPLACED IAW SRM 51-30-02 AND 51-30-05.

Part: FLOOR SUPPORT — GOUGED (FUSELAGE) · airframe 42,261 hrs · 20,007 cycles

INSPECTION FOUND SUBFLOOR GOUGED AT FS 150, LBL 50. THE GOUGED WAS BLENDED OUT IAW SRM 53-01, FIGURE 1 AND A DOUBLER WAS INSTALLED IAW SRM 53-01, FIGURE 4, 53-14-01, AND 51-30-02.

Part: POWER SUPPLY — INOPERATIVE (GALLEY) · airframe 42,037 hrs · 19,890 cycles

OVERHEAD EMERGENCY LIGHTS INOP AT FORWARD GALLEY AND F/C CLOSET. REMOVED AND REPLACED POWER SUPPLY.

Part: BATTERIES — DISCHARGED (EMER EXIT)

INSPECTION FOUND OVERHEAD EMERGENCY LIGHTS INOPERATIVE IN FIRST CLASS SECTION OF CABIN. THE BATTERIES WERE REPLACED IN THE BATTERY PACK AND OPERATION CHECKED GOOD.

Part: SKIN — CORRODED (WS 295 & 310)

INSPECTION FOUND LT WING SKIN PANEL LOWER SIDE CORRODED AT STA XRS 295 AND 310. THE CORROSION WAS REMOVED AND A REPAIR DOUBLER WAS INSTALLED IAW SRM 57-03, FIGURE 24A.

Part: SKIN — CORRODED (LT HORIZ STAB)

LEFT HORIZ STAB LOWER AFT SKIN PANEL NR 3 FOUND CORROSION BETWEEN STA XHS86 AND XHS104. INSTALLED REPAIR DOUBLERS PER EC/RA 5510-01409.

Part: TIE DOWN RAIL — CORRODED (BS 1007-1155)

AFT CARGO BIN RIGHT SIDE TIE DOWN RAIL STA 1007 TO 1155 CORRODED AT FASTENERS. INSTALLED NEW TIE DOWN RAIL PER SRM 51-30.

Part: JAMB — CORRODED (BS 670-690)

MID CARGO BIN DOOR JAMB BEAM (Z ANGLE) HAS SURFACE CORROSION FROM STA 670 TO 690. BURNISHED CORROSION AND INSTALLED REPAIR DOUBLER UNDER FWD LOWER DOOR STOP PER EC/RA 5310-03723.

Part: TIE DOWN RAIL — CORRODED (BS 1007-1220)

AFT CRGO BIN LEFT TIE DOWN RAIL STA 1007 TO 1220 CORRODED AT FASTENERS. REPLACED LEFT TIE DOWN RAIL PER SRM 51-30-5.

Part: BELTFRAME — CORRODED (BS 1309)

AFT CARGO BIN BELTFRAME CORRODED STA 1309 LONG 28 LT TO 28 RT. REMOVED AND REPLACED CORRODED SECTION OF BELTFRAME PER SRM 53-03 FIG 2A.

Part: RIGGING — OUT OF RIG (TAIL CONE)

FORCE REQUIRED TO PULL INTERIOR TAIL CONE RELEASE HANDLE IS TO LOW. RIGGED HANDLE PER MM 53-53-00.

Part: CABLE — FRAYED (TAIL CONE)

FORCE REQUIRED TO RELEASE TAIL CONE TO HIGH. REPLACED CABLE, RIGGED TAIL CONE PER MM 53-53-00 AND FUNCTIONAL CHECKED.

Part: HOUSING — WORN (L1 DOOR)

MAIN CABIN DOOR HOLD OPEN HOOK WELL WORN INTO BY HOOK AND SKIN AROUND LOWER EDGE OF HOOK WELL OPENING DAMAGED FORWARD FUSELAGE. BURNISHED MAIN CABIN DOOR SKIN AND REPLACED HOLD OPEN HOOK HOUSING PER SRM 51-30-2.

Part: BEAM — CRACKED (FUSELAGE)

F/S/D NR 4 BEAM IS CRACKED AT FORWARD END APPROX 1. REMOVED CRACKED BEAM AND INSTALLED SERVICEABLE PER SRM 51-30-2 AND 51-30-5.

Part: SKIN — DAMAGED (BS 1098)

TEMP REPAIR ON AIRPHONE ANTENNA AT STA 1098. REPAIRED PER SRM 53-04 AND EC/RA 5330-02657.

Part: INTERCOSTAL — CRACKED (PAX DOOR)

MAIN CABIN DOOR INTERCOSTAL AFT OF DOOR LOCK MECHANISM IS CRACKED (1) WHERE IT ATTACHES TO OUTSIDE HANDLE RECESS. INSTALLED NEW INTERCOSTAL PER SRM 51-30-2.

Part: SKIN — DAMAGED (BS 1117)

TEMP REPAIR ON AIRPHONE ANTENNA AT STA 1117. REPLACED PER SRM 53-04 AND EC/RA 5330-02657.

Part: HYD LINE — BROKEN (LT T/R PRESS SW)

THE LT HYDRAULIC QUANTITY GAUGE DROPPED TO ZERO WITH THE LEFT HYDRAULIC PRESSURE AND LEFT BRAKE PRESSURE ALSO AT ZERO AFTER TOUCHDOWN AT EWR. MAINTENANCE FOUND THE LT THRUST REVERSER HYDRAULIC PRESSURE SWITCH LINE BROKEN. THE LINE WAS REMOVED AND REPLACED. THE HYDRAULIC SYSTEM WAS SERVICED TO FULL. LEAK CHECK AND AN OPERATIONAL CHECK OF THE LT THRUST REVERSER WERE GOOD.

Part: HYD LINE — LEAKING (TAIL SECTION)

SMOKE FILLED CABIN DURING TAXI TO GATE AT IAH. THE AIRCRAFT STOPPED ON SOUTH PAD AND BOTH ENGINES AND THE APU WERE SHUT DOWN. PASSENGERS WERE DEPLANED THROUGH AFT AIRSTAIRS. MAINTENANCE FOUND A HYDRAULIC LEAK IN TAIL SECTION ALLOWING HYDRAULIC FLUID TO BE SUCKED INTO THE APU AND PACKS RESULTING IN THE CABIN SMOKE. THE HYDRAULIC LINE IN LEFT HYDRAULIC SYSTEM WAS REPLACED. A BURN OUT PROCEDURE WAS PERFORMED IAW MM 21-20-02. IN ADDITION, THE WATER SEPARATOR SOCKS WERE REPLACED.

Part: HYD LINE — BROKEN (LT THRUST REVER)

THE LEFT HYDRAULIC SYSTEM QUANTITY AND PRESSURE DROPPED TO ZERO AND THE CABIN FILLED WITH SMOKE DURING LANDING ROLLOUT. THE PACKS AND BLEEDS WERE CLOSED AND CABIN DOORS WERE OPENED TO CLEAR SMOKE. THE AIRCRAFT WAS TOWED TO THE GATE. MAINTENANCE FOUND THE LINE TO THRUST REVERSER LOW PRESSURE SWITCH BROKEN. THE LINE WAS REPLACED AND LEAK CHECK WAS GOOD.

Part: OVEN — CONTAMINATED (FWD GALLEY)

SMOKE WAS OBSERVED COMING FROM THE FORWARD GALLEY WHILE EN ROUTE. THE FORWARD OUTBOARD OVEN WAS FOUND TO BE EXTREMELY HOT. THE OVEN CIRCUIT BREAKERS WERE DEACTIVATED AND THE SMOKE CEASED. THE AIRCRAFT WAS DIVERTED TO GSO WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND BURNED PLASTIC MATERIAL IN RACK OF FORWARD GALLEY OUTBOARD OVEN. THE OVEN WAS PLACARDED INOPERATIVE, NO OTHER DEFECTS WERE FOUND.

Part: SKIN — DENTED (BS 256)

INSPECTION FOUND THE LT FUSELAGE SKIN DENTED IN TWO PLACES AT STA 256. ONE DENT WAS LOCATED BELOW DOUBLER BETWEEN LONGERON 17 AND 18. THE OTHER WAS AFT OF DOUBLER BETWEEN LONGERON 17 AND 18. THE DENTED AREAS WERE REMOVED, DOUBLERS WERE FABRICATED AND INSTALLED IAW SRM 51-30-2 AND ECRA 5330-01203.

Part: SUBFLOOR — CORRODED (BS 168-200)

INSPECTION FOUND CABIN SUBFLOOR AT FORWARD SERVICE DOOR CORRODED FROM FS 168 TO 200. A NEW WEB SECTION WAS FABRICATED AND INSTALLED IAW SRM 51-10-2.

Part: FLOOR WEB — CORRODED (BS 200)

INSPECTION FOUND FLOOR WEB CORRODED AT STA 200, LBL 8. THE CORRODED AREA WAS CUT OUT, A REPAIR WAS FABRICATED AND INSTALLED IAW SRM 53-01.

Part: SKIN — CRACKED (RT WING LE)

INSPECTION FOUND A .3125 INCH CRACK IN SKIN AT FORWARD OUTBOARD CORNER OF RIGHT WING FUELING STATION DOOR CUTOUT. THE CRACK WAS STOP DRILLED AND A REPAIR DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 57-06B.

Part: SKIN — DENTED (BS 256)

INSPECTION FOUND THE LT FUSELAGE SKIN DENTED FORWARD OF STA 256 AT LONGERON 17. A DOUBLER WAS FABRICATED AND INSTALLED IAW SRM 53-04, FIGURE 38, SHEET 19.

Part: SKIN — DENTED (NR 1 LE FLAP)

INSPECTION FOUND TWO DENTS IN NR 1 RT SLAT LEADING EDGE. A REPAIR WAS INSTALLED IAW SRM 57-06, FIGURE 1 AND ECRA 5720-01170.

Part: PROX SWITCH — INOPERATIVE (LT MLG)

FLT NR 1823 - IAH - THE LT GEAR UNSAFE LIGHT AND GEAR DOOR OPEN LIGHT REMAINED ILLUMINATED AFTER GEAR RETRACTION DEPARTING IAH. THE AUTO SPOILER 'DO NOT USE' LIGHT WAS ALSO ON. CYCLING THE GEAR DID NOT HELP. THE AIRCRAFT WAS RETURNED TO IAH WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE LEFT MLG AND DOOR LATCH PROXIMITY SWITCH INOPERATIVE. THE PROXIMITY SWITCH WAS REMOVED AND REPLACED. AN OPERATIONAL CHECK WAS PERFORMED AND SWITCH FUNCTION WAS GOOD. THE AUTO SPOILER SYSTEM WAS RESET AND THE LIGHT EXTINGUISHED. (M)

Part: AIR DISTR — SMOKE (CABIN)

FLT NR 1623 - CLE - SMOKE APPEARED IN THE CABIN AND COCKPIT ON FINAL APPROACH TO CLE. MAINTENANCE REPLACED BOTH WATER SEPARATOR BAGS AND NOTED PACK DUCTING WAS DRY OF FLUID. THE ENGINE SADDLE DUCTS WERE INSPECTED FOR OIL AND NONE WAS FOUND. THE GEAR WAS PINNED AND THE GEAR HANDLE, FLAPS, AND THRUST REVERSER WWERE CYCLED SEVERAL TIMES WITH NO LEAKS NOTED. A HIGH POWER RUN WAS CONDUCTED WHILE THE AIR CONDITIONING SYSTEM WAS CYCLED HOT AND COLD SEVERAL TIMES OVER A PERIOD OF ABOUT ONE HOUR. NO INDICATIONS OF SMOKE OR SMELL WERE FOUND. THE ANOMALY COULD NOT BE DUPLICATED. (M)

Part: DNLOCK SENSOR — INOPERATIVE (NLG)

FLT NR 1821 - SEA - THE NLG RED LIGHT REMAINED ILLUMINATED AFTER GEAR RETRACTION ON TAKEOFF FROM SEA. THE COCKPIT NLG INDICATOR PIN INDICATED THE GEAR WAS IN TRANSIT. CYCLING THE GEAR DID NOT HELP. THE AIRCRAFT WAS RETURNED TO SEA WHERE IT LANDED WITHOUT INCIDENT. THE NOSE GEAR STRUT WAS SERVICED. A NOSE GEAR RETRACT WAS PERFORMED, BUT THE PROBLEM REMAINED. MAINTENANCE FOUND THE NOSE GEAR DOWNLOCK SENSOR AT FAULT DURING A GEAR PROXIMITY SENSOR BITE CHECK. THE SENSOR WAS REMOVED AND REPLACED. A NOSE GEAR RETRACTION WAS PERFORMED WITH OPERATION AND INDICATIONS CHECKING GOOD. (M)

Part: FUEL CONTROL — INOPERATIVE (APU)

SLC - FLT 0288 - WHILE OPERATING THE APU AT CRUISE WITH THE LEFT GENERATOR SYSTEM PLACARDED INOPERATIVE, THE APU RPM SLOWLY INCREASED THROUGH 104 PERCENT TO 105 PERCENT AND THEN SHUT DOWN. THE AIRCRAFT WAS DIVERTED TO SLC WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE RAN THE APU AND ALL PARAMETERS WERE WITHIN LIMITS. THE APU WAS RESTARTED SEVERAL TIMES AND RAN AT 103 PERCENT DURING ALL RUNS. THE APU CONTINUED TO HAVE PROBLEMS ON A SUBSEQUENT FERRY FLIGHT. THE APU FUEL CONTROL UNIT WAS REMOVED AND REPLACED AND OPERATION OF THE APU CHECKED NORMAL. (X)

Part: OIL LINE — CRACKED (NR 1 ENGINE)

FLT NR 0424 - JFK - THE NR 1 ENGINE OIL QUANTITY BEGAN TO DROP IN FLIGHT WITH AN ASSOCIATED DROP IN PRESSURE. THE NR 1 ENGINE WAS SHUT DOWN. WHILE ON APPROACH TO EWR WINDSHEAR WAS ENCOUNTERED, APPROACH WAS ABORTED AND AIRCRAFT WAS DIVERTED TO JFK WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 1 ENGINE OIL LINE TO DIFFERENTIAL PRESSURE SWITCH CRACKED. THE LINE WAS CAPPED OFF. A DECISION WAS MADE TO REPLACED THE NR 1 ENGINE AS A PRECAUTIONARY MEASURE DUE TO HISTORY OF OIL LOSS ON THIS ENGINE. (M)

Part: OIL LINE — CRACKED (NR 1 ENGINE)

FLT NR 0133 - CLE - THE LEFT OIL STRAINER CLOG LIGHT CAME ON WHILE EN ROUTE FROM LGA TO IAH. THE FLIGHT WAS DIVERTED TO CLE. THE LIGHT WENT OUT DURING DESCENT AT LOW POWER, BUT CAME BACK ON DURING FINAL APPROACH. THE LEFT ENGINE OIL QUANTITY WAS SLOWLY DECREASING. THE AIRCRAFT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND THE NR 1 ENGINE OIL PRESSURE SWITCH LINE CRACKED. THE OIL LINE WAS REMOVED AND REPLACED AND LEAK CHECK WAS GOOD. (M)

Part: LINE — CRACKED (PRESS SWITCH)

MCO - FLT 0678 - THE LEFT ENGINE OIL STRAINER CLOGGING LIGHT ILLUMINATED IN-FLIGHT. THE ENGINE WAS REDUCED TO FLIGHT IDLE AND THE LIGHT EXTINGUISHED, BUT CAME ON AGAIN WITH POWER. THE AIRCRAFT WAS RETURNED TO MCO WITH ENGINE AT FLIGHT IDLE AND WITH THE OIL CLOG LIGHT EXTINGUISHED. MAINTENANCE FOUND THE LEFT ENGINE OIL LINE TO THE DIFFERENTIAL PRESSURE SWITCH CRACKED. THE OIL LINE WAS REPLACED. THE LEFT ENGINE WAS RUN AND LEAK CHECK WAS GOOD AND THE OIL CLOG LIGHT REMAINED OUT. (X)

Part: LINE — CRACKED (OIL PRESS SWITCH)

LAS - FLT 0724 - THE NR 1 ENGINE OIL FILTER CLOG LIGHT ILLUMINATED, ACCOMPANIED BY A LOSS OF OIL WHILE IN-FLIGHT. THE AIRCRAFT WAS RETURNED TO LAS WHERE IT LANDED WITHOUT INCIDENT. MAINTENANCE FOUND LINE TO LOW OIL PRESSURE SWITCH CRACKED. THE LINE WAS REMOVED AND REPLACED. LEAK AND OPERATIONAL CHECKS WERE GOOD. (X)